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Wings shape effect on behavior of hybrid nanofluid inside a channel having vortex generator

  • Ghanbar Ali Sheikhzadeh
  • Faezeh Nejati Barzoki
  • Ali Akbar Abbasian Arani
  • Farzad Pourfattah
Original

Abstract

Thermal and flow characteristics of hybrid nanofluid inside a channel having vortex-generator with different wing shapes, is investigated numerically. Three different wing shapes, including rectangular, triangular, and trapezoidal, are considered. The geometrical configuration considered in this work is representative of a channel with three wings in each row; one mounted to the top plate and the other ones mounted to the bottom plate and this trend changes between the plates alternately. MgO-MWCNT (50:50) suspended in the ethylene glycol (EG) as base fluid with volume fractions of 0.1%, 0.2%, 0.4%, and 0.6% is considered as working fluid. The effects of volume fraction of the nanoparticles and type of wings in the Reynolds number range of 200–1600, are investigated. Heat transfer coefficient, pressure drop and performance evaluation criterion (PEC) are the most important parameters that investigated at different flow conditions. The results shown that rectangular wings leads to increase the heat transfer coefficient. In addition the channel with trapezoidal and triangular wings at the same volume fraction, have the higher values of PEC due to lower pressure drop. Also the result indicated that heat transfer coefficient are enhanced by increasing the nanoparticles volume fraction. According to obtained results, the trapezoidal wings with nanofluid volume of fraction of 0.6 and minimum Reynolds number leads to desirable performance from heat transfer and fluid flow viewpoint.

Nomenclature

Ac

minimum free flow area (m2)

At

total surface area in contact with working fluid (m2)

Cp

specific heat (J kg-1 K-1)

Dh

hydraulic diameter (m)

Fh

fin height (m)

FP

fin pitch (m)

h

effective heat transfer coefficient (W m-2 K-1)

k

turbulent kinetic energy

L

channel length (m)

\( \dot{m} \)

mass flow rate (kg s-1)

nt

number of tabs

\( \dot{Q} \)

convective heat transfer rate (W)

Rh

rectangular wing height (m)

Rw

rectangular wing width (m)

T

temperature (K)

Th

triangular wing height (m)

Tw

triangular wing width (m)

T

fin thickness (m)

U

velocity (m s-1)

Vl

longitudinal vortex spacing (m)

Vt

transverse vortex spacing (m)

wh

trapezoidal wing height (m)

∆P

pressure drop (Pa)

∆T

temperature difference (K)

x,y,z

Cartesian coordinates

Greek symbols

ρ

density (kg m-3)

μ

dynamic viscosity (kg m-1 s-1)

λ

thermal conductivity (W m-1 K-1)

φ

solid volume fraction

δ

Kronecker delta

σK

effective Prandtl number

σε

Schmidt number

ε

rate of dissipation

Subscripts

ave

average

b

Bulk

bf

base fluid

conv

Convective

f

Fluid

i,j

x direction, y direction

LMTD

Logarithmic Mean Temperature Difference

in

inlet

nf

Nanofluid

out

outlet

w

Wall

Dimensionless groups

f

friction factor

Nu

Nusselt number

PEC

performance evaluation criterion

Re

Reynolds number

Notes

Acknowledgements

The authors wish to thank the Energy Research Institute and the Research & Technology Administration of the University of Kashan for their support regarding this research (Grant No. 785398).

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Copyright information

© Springer-Verlag GmbH Germany, part of Springer Nature 2018

Authors and Affiliations

  • Ghanbar Ali Sheikhzadeh
    • 1
  • Faezeh Nejati Barzoki
    • 1
  • Ali Akbar Abbasian Arani
    • 1
  • Farzad Pourfattah
    • 2
  1. 1.Mechanical Engineering DepartmentUniversity of KashanKashanIran
  2. 2.Mechanical and Aerospace Engineering DepartmentMalek-Ashtar University of TechnologyIsfahanIran

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